Cmc combustor shell with integral chutes

ABSTRACT

A combustion assembly for a gas turbine engine may be provided. The combustion assembly may include a ceramic matrix composite combustor shell, which may include a chamber defined by a wall of the ceramic matrix composite combustor shell, and the ceramic matrix composite combustor shell may include a ceramic matrix composite chute integral with the ceramic matrix composite combustor shell. The ceramic matrix composite chute may extend towards a midline of the chamber. A method for fabricating a ceramic matrix composite chute may be provided. At least one chute may be woven in three dimensions into a ceramic preform. A layup tool may be inserted into the chute. The chute may be enlarged with the layup tool. The ceramic preform may be formed into a ceramic matrix composite body, which includes a combustor shell and the chute.

TECHNICAL FIELD

This disclosure relates to ceramic matrix composite (CMC) componentsand, in particular, to CMC combustor shells.

BACKGROUND

Present approaches to attaching chutes to ceramic matrix compositecombustor shells suffer from a variety of drawbacks, limitations, anddisadvantages. There is a need for the inventive ceramic matrixcomposite components, apparatuses, systems and methods disclosed herein.

BRIEF SUMMARY

A combustion assembly for a gas turbine engine may be provided. Thecombustion assembly for the gas turbine engine may include a ceramicmatrix composite combustor shell. The ceramic matrix composite combustorshell may include a chamber defined by a wall of the ceramic matrixcomposite combustor shell and a ceramic matrix composite chute integralwith the ceramic matrix composite combustor shell. The ceramic matrixcomposite chute may extend towards a midline of the chamber of theceramic matrix composite combustor shell.

A method for fabricating a ceramic matrix composite chute may beprovided. A porous ceramic preform comprising a plurality of ceramicfibers may be formed. An aperture in the porous ceramic preform may beformed. The aperture may be enlarged into a chute shape by inserting alayup tool into the aperture. The porous ceramic preform may be formedinto a ceramic matrix composite body, which includes a combustor shelland a chute.

Another method for fabricating a ceramic matrix composite chute may beprovided. A ceramic preform may be formed into a frame for a combustorshell and a chute. The ceramic preform may be formed into a ceramicmatrix composite body including the combustor shell and the chute. Anaperture in the ceramic preform may be enlarged with a layup tool.

BRIEF DESCRIPTION OF THE DRAWINGS

The embodiments may be better understood with reference to the followingdrawings and description. The components in the figures are notnecessarily to scale. Moreover, in the figures, like-referenced numeralsdesignate corresponding parts throughout the different views.

FIG. 1 illustrates a cross-sectional view of a combustion assembly for agas turbine engine;

FIG. 2 illustrates a plan view of an example of a ceramic preformcomprising a plurality of ceramic fibers;

FIG. 3 illustrates a plan view of another example of a ceramic preformcomprising a plurality of ceramic fibers;

FIG. 4 illustrates a cross-sectional view of an example of a ceramicmatrix composite body; and

FIG. 5 illustrates a cross-sectional view of a ceramic preform and chuteand a layup tool.

FIG. 6 illustrates another cross-sectional view of a combustion assemblyfor a gas turbine engine;

FIG. 7 illustrates a flow chart of a method for fabricating a ceramicmatrix composite chute.

FIG. 8 illustrates a flow chart of another method for fabricating aceramic matrix composite chute.

DETAILED DESCRIPTION

By way of introduction, in one example, a combustion assembly for a gasturbine engine may be provided. The combustion assembly may include aceramic matrix composite combustion liner that attaches to a combustorand is located in a chamber of the combustor. The ceramic matrixcomposite combustion liner may alternatively be referred to herein as aceramic matrix composite liner or liner. The chamber may be defined by awall of the combustor and the ceramic matrix composite liner may includea ceramic matrix composite chute integral with the ceramic matrixcomposite liner. The ceramic matrix composite chute may extend towards amidline of the chamber of the combustor.

Advantageously, the ceramic matrix composite chute may direct mixing airso that the mixing performance of the combustor is enhanced. Byfabricating the ceramic matrix composite chute integral with the ceramicmatrix composite liner, any difficulties in attaching chutes to ceramicmatrix composite liners may be avoided. Fabricating the ceramic matrixcomposite chute integral with the ceramic matrix composite liner mayallow a variety of chute shapes to be used.

FIG. 1 is a cross-sectional view of a combustion assembly 2 for a gasturbine engine. The gas turbine engine may be an internal combustionengine that has an upstream rotating compressor coupled to a downstreamturbine, and a combustor 10 in between. The combustion assembly 2 may bea component capable of withstanding high temperatures, for exampletemperatures above 1000 degrees Celsius. The combustion assembly 2 mayinclude, for example, the combustor 10, a ceramic matrix composite liner20, and a ceramic matrix composite chute 30. In some examples, thecombustion assembly 2 may include a ceramic matrix composite coating, anenvironmental barrier coating, or a combination thereof.

The combustor 10 may comprise a wall 12 that defines a chamber 14. Thecombustor 10 may be a portion of the gas turbine engine where combustiontakes place. The combustor 10 may be a component in which fuel isignited in the gas turbine engine. In some examples, the combustor 10may be a component in which air and fuel are combined and ignited.Examples of the combustor 10 may include a can, cannular, annular, ordouble annular combustor.

The ceramic matrix composite liner 20 may be a component made of aceramic matrix composite material that covers an inner surface of thecombustor 10. The ceramic matrix composite liner 20 may cover the wall12 of the combustor 10. In some examples, the ceramic matrix compositeliner 20 may at least partially cover the wall 12 of the combustor 10.The ceramic matric composite liner 20 may or may not be in contact withthe wall 12 of the combustor 10. The ceramic matrix composite liner 20may include ceramic fibers 22, as shown in FIGS. 2-3. Examples of theceramic fibers 22 may include fibers of alumina, mullite, siliconcarbide, zirconia, or carbon.

The ceramic matrix composite chute 30 may be a passage through whichfluid, such as air, may pass. The ceramic matrix composite chute 30 maybe in a form of a tube that is open at both ends of the tube.Alternatively, the ceramic matrix composite chute 30 may be in any othershape through which the passage may channel fluid. The ceramic matrixcomposite chute 30 may extend towards a midline 16 of the chamber 14 ofthe combustor 10. The ceramic matrix composite chute 30 may extend up toone inch towards the midline 16 of the chamber 14 of the combustor 10.The midline 16 may be a line that passes through the center of thecombustor 10 in an axial direction and spans the combustor. The ceramicmatrix composite chute 30 may define a chute opening 31 into the chamber14 that is in a plane substantially parallel with a plane that istangent to the ceramic matrix composite liner 20 where the ceramicmatrix composite chute 30 and the ceramic matrix composite liner 20intersect. Alternatively or in addition, the chute opening 31 may bescarfed, as shown in FIG. 4. The scarfed chute opening 31 may be anopening defined by a tapered end of the chute 30. The scarfed chuteopening 31 may be formed by, for example, cutting a tapered end on thechute 30. Alternatively or in addition, the opening 31 of the ceramicmatrix composite chute 30 may include a cross-sectional profile of acircle, oval, square, rectangle, trapezoid, or other shape. Like ceramicmatrix composite liner 20, the ceramic matrix composite chute 30 maycomprise ceramic fibers 22, as shown in FIGS. 2-3. Examples of theceramic fibers 22 may include fibers of alumina, mullite, siliconcarbide, zirconia, or carbon.

The ceramic matrix composite chute 30 may be integral with the ceramicmatrix composite liner 20. In other words, the ceramic matrix compositechute 30 and the ceramic matrix composite liner 20 may be one continuouspiece. The ceramic matrix composite chute 30 and the ceramic matrixcomposite liner 20 may be formed from a single ceramic preform 34, asshown in FIG. 2, resulting in one continuous piece without any seamsbetween the ceramic matrix composite chute 30 and the ceramic matrixcomposite liner 20. Methods of forming the ceramic matrix compositechute 30 integral to the ceramic matrix composite liner 20 are describedfurther below.

During operation of the combustion assembly 2, the ceramic matrixcomposite chute 30 directs mixing air into the chamber 14 of thecombustor 10. The flow of mixing air is shown by arrow A in FIG. 1. As aresult of the ceramic matrix composite chute 30 extending towards themidline 16 of the chamber 14 of the combustor 10, the flow of mixing airmay avoid an axial flow of air passing through the chamber 14 of thecombustor 10 and approach the midline 16 of the chamber 14 of thecombustor 10. In other words, the chute 30 channels the mixing airtoward the midline 16 allowing the mixing air to mix with fuel near themidline 16, resulting in more efficient combustion. Without the chute 30extending towards the midline 16 of the chamber 14 of the combustor 10,the mixing air may not reach the fuel near the midline 16.

FIGS. 2 and 3 are plan views of examples of the ceramic preform 34comprising a plurality of ceramic fibers 22. The ceramic preform 34 maybe an arrangement of the ceramic fibers 22. The arrangement may be fixedin a desired shape. The arrangement of the ceramic fibers 22 may be aframe. The ceramic preform 34 is porous. Examples of the ceramic preform34 may include a three-dimensional weave of the ceramic fibers 22.Alternatively or in addition, the ceramic preform 34 may include atwo-dimensional weave of the ceramic fibers 22. The ceramic preform 34may include multiple stacked layers of two-dimensional weaves of theceramic fibers 22. Alternatively or in addition, the ceramic preform 34may include a fiber layup, such as a unidirectional layup. The ceramicpreform 34 may include multiple stacked layers of unidirectional layupsof the ceramic fibers 22.

In some examples, each of the ceramic fibers 22 may be a bundle and/or atow of ceramic fibers. The fibers in each bundle or tow may be braidedor otherwise arranged.

The ceramic fibers 22 may comprise a material that is stable attemperatures above 1000 degrees Celsius. Examples of the ceramic fibers22 may include fibers of alumina, mullite, silicon carbide, zirconia orcarbon. The ceramic fibers 22 may not be organic, metallic or glassfibers.

FIG. 4 is a cross-sectional view of an example of a ceramic matrixcomposite body 50. The ceramic matrix composite body 50 may comprise thecombustion liner 20 and the chute 30 as one continuous piece. Theceramic matrix composite chute 30 may define the chute opening 31, whichmay be scarfed.

FIG. 5 is a cross-sectional view of the ceramic preform 34 and chute 30and a layup tool 40. The ceramic preform 34 may be formed into a frame36 for the combustion liner 20 and the chute 30. The frame 36 may be anunderlying structure that gives shape or strength.

FIG. 6 is a cross-sectional view of another embodiment of a combustionassembly 602 for a gas turbine engine. The combustion assembly 602 maybe a component capable of withstanding high temperatures, for exampletemperatures above 1000 degrees Celsius. The combustion assembly 602 mayinclude, for example, a ceramic matrix composite combustor shell 690 anda ceramic matrix composite chute 630. In some examples, the combustionassembly 602 may include a ceramic matrix composite coating, anenvironmental barrier coating, or a combination thereof.

The ceramic matrix composite combustor shell 690 may comprise a wall 612that defines a chamber 614. The ceramic matrix composite combustor shell690 may be a ceramic matrix composite combustor with no metal backbone,a full annular ceramic matrix composite heat shield, or a ceramic matrixcomposite combustor tile. The full annular ceramic matrix composite heatshield may be a one piece ceramic matrix composite heat shield attachedto a metal support structure and/or combustor. The ceramic matrixcomposite combustor tile may be one or more ceramic matrix compositepieces attached to a metal support structure and/or combustor.

The ceramic matrix composite combustor shell 690 may include ceramicfibers 22, as shown in FIGS. 2-3. Examples of the ceramic fibers 22 mayinclude fibers of alumina, mullite, silicon carbide, zirconia, orcarbon.

The ceramic matrix composite chute 630 may be a passage through whichfluid, such as air, may pass. The ceramic matrix composite chute 30 maybe in a form of a tube that is open at both ends of the tube.Alternatively, the ceramic matrix composite chute 630 may be in anyother shape through which the passage may channel fluid. The ceramicmatrix composite chute 630 may extend towards a midline 616 of thechamber 614. The ceramic matrix composite chute 630 may extend up to oneinch towards the midline 616 of the chamber 614. The midline 616 may bea line that passes through the center of the ceramic matrix compositecombustor shell 690 in an axial direction and spans the combustor. Theceramic matrix composite chute 630 may define a chute opening 631 intothe chamber 614 that is in a plane substantially parallel with a planethat is tangent to the ceramic matrix composite combustor shell 690where the ceramic matrix composite chute 630 and the ceramic matrixcomposite combustor shell 690 intersect. Alternatively or in addition,the chute opening 631 may be scarfed. The scarfed chute opening 631 maybe an opening defined by a tapered end of the chute 630. The scarfedchute opening 631 may be formed by, for example, cutting a tapered endon the chute 630. Alternatively or in addition, the opening 631 of theceramic matrix composite chute 630 may include a cross-sectional profileof a circle, oval, square, rectangle, trapezoid, or other shape. Likeceramic matrix composite combustor shell 690, the ceramic matrixcomposite chute 630 may comprise ceramic fibers 22, as shown in FIGS.2-3. Examples of the ceramic fibers 22 may include fibers of alumina,mullite, silicon carbide, zirconia, or carbon.

The ceramic matrix composite chute 630 may be integral with the ceramicmatrix composite combustor shell 690. In other words, the ceramic matrixcomposite chute 630 and the ceramic matrix composite combustor shell 690may be one continuous piece. The ceramic matrix composite chute 630 andthe ceramic matrix composite combustor shell 690 may be formed from asingle ceramic preform 34, as shown in FIG. 2, resulting in onecontinuous piece without any seams between the ceramic matrix compositechute 630 and the ceramic matrix composite combustor shell 690. Methodsof forming the ceramic matrix composite chute 630 integral to theceramic matrix composite combustor shell 690 are described furtherbelow. The methods of forming the ceramic matrix composite chute 630integral to the ceramic matrix composite combustor shell 690 are thesame whether the ceramic matrix composite chute 630 is integral to theceramic matrix composite combustor with no metal backbone, the fullannular ceramic matrix composite heat shield, or the ceramic matrixcomposite combustor tile.

During operation of the combustion assembly 602, the ceramic matrixcomposite chute 630 directs mixing air into the chamber 614. The flow ofmixing air is shown by arrow B in FIG. 6. As a result of the ceramicmatrix composite chute 630 extending towards the midline 616 of thechamber 614, the flow of mixing air may avoid an axial flow of airpassing through the chamber 614 and approach the midline 616 of thechamber 614. In other words, the chute 630 channels the mixing airtoward the midline 616 allowing the mixing air to mix with fuel near themidline 616, resulting in more efficient combustion. Without the chute630 extending towards the midline 616 of the chamber 614, the mixing airmay not reach the fuel near the midline 616.

FIG. 7 illustrates a flow chart of an example method for fabricating theceramic matrix composite chute 30. The method may include additional,fewer, or different steps than illustrated in FIG. 7.

First, the ceramic preform 34 may be formed (710) into the ceramicpreform 34. Next, the aperture 32 may be formed (720) in the ceramicpreform 34. The aperture 32 may be enlarged (730) into the chute shapeby inserting the layup tool 40 into the aperture 32. Finally, theceramic preform 34 may be formed (740) into the ceramic matrix compositebody 50 that comprises the combustion liner 20 and the chute 30. Moregenerally, the ceramic preform 34 may be formed into the ceramic matrixcomposite body 50 that comprises the ceramic matrix composite combustorshell 690 and the chute 30.

In some examples, forming the porous ceramic preform 34 comprising theceramic fibers 22 may include shaping the ceramic fibers 22 into adesired shape. Forming the porous ceramic preform 34 may includeconfiguring the ceramic fibers 22 into one or more shapes. Alternativelyor in addition, forming the porous ceramic preform 34 may includestacking two-dimensional weaves or unidirectional tape layups, orweaving the ceramic fibers 22 in three dimensions.

In some examples, forming the aperture 32 in the porous ceramic preform34 may include leaving a gap in the porous ceramic preform 34. Formingthe aperture 32 in the porous ceramic preform 34 may include cutting ahole in the porous ceramic preform 34. Forming the aperture 32 in theporous ceramic preform 34 may include forming an opening in eachtwo-dimensional weave or unidirectional tape layup and aligning theopenings in the stacked plurality of two-dimensional weaves orunidirectional tape layups. Forming the aperture 32 in the porousceramic preform 34 may include weaving the aperture 32 into the porousceramic preform 34.

In some examples, enlarging the aperture 32 into the chute shape byinserting the layup tool 40, as shown in FIG. 5, into the aperture 32may include shaping the aperture 32 into the larger chute shape with thelayup tool 40. Enlarging the aperture 32 into the chute shape byinserting the layup tool 40 into the aperture 32 may include pressingthe layup tool 40 into the aperture 32 until the larger chute shaperemains. The layup tool 40 may be a material that shapes the porousceramic preform 34. The layup tool 40 may be the inverse of the desiredchute shape. The layup tool 40 may create a chute shape with the chuteopening 31 that is substantially parallel with the combustion liner 20or with the ceramic matrix composite combustor shell 690. Alternativelyor in addition, the layup tool 40 may create a chute shape from thechute opening 31 that is scarfed

In some examples, forming the porous ceramic preform 34 into the ceramicmatrix composite body 50, as shown in FIG. 4, may include infiltrating amolten metal or alloy (for example, a silicon metal or alloy) into theceramic preform 34. The silicon metal or alloy may fill gaps between theceramic fibers 22. The silicon metal or alloy may also react with areactive element source present in the ceramic preform 34 to formadditional silicon based ceramic matrix material. In some examples, achemical vapor infiltration coating may be applied to the ceramicpreform 34 prior to the melt infiltration to stiffen the ceramic fibers22. Alternatively or in addition, forming the ceramic matrix compositebody 50 from the ceramic preform 34 may include chemical vaporinfiltrating the ceramic preform 34 instead of melt infiltrating amaterial into the ceramic preform 34.

Prior to melt infiltration and/or chemical vapor infiltration, theceramic matrix composite body 50 may be formed by a slurry infiltrationprocess. A slurry comprising a solvent and the solid particulate mattermay be infiltrated into the ceramic preform 34 assembled from siliconcarbide fibers. Prior to introducing the slurry, the ceramic preform 34may be exposed to a vacuum, and the vacuum may be removed duringinfiltration to create a pressure gradient (for example, about 1 atm)that forces slurry into the preform. The infiltration may be carried outat room temperature (for example, from about 15° C. to about 25° C.).After infiltration, the ceramic matrix composite body 50 may be dried toremove the solvent. Drying may be carried out at room temperature or atan elevated temperature (for example, from about 40° C. to about 150°C.). Typically, slurry infiltration leads to a loading level of solidparticulate matter in the ceramic matrix composite body 50 of from about40 vol. % to about 60 vol. %, with the remainder being porosity.Alternatively or in addition, forming the ceramic matrix composite body50 from the ceramic preform 34 may include slurry infiltrating theceramic preform 34 instead of melt infiltrating a material into theceramic preform 34.

FIG. 8 illustrates a flow chart of a second example method forfabricating the ceramic matrix composite chute 30. The method mayinclude additional, fewer, or different steps than illustrated in FIG.8.

First, the ceramic preform 34 may be formed (810) into the frame 36 forthe combustion liner 20 and the chute 30. Next, the ceramic preform 34may be formed (820) into the ceramic matrix composite body 50. Finally,the aperture 32 may be enlarged (830) in the ceramic preform 34 with thelayup tool 40.

In some examples, forming the ceramic preform 34 may include shaping theceramic preform 34 into a desired shape. The ceramic preform 34 may beformed into the frame 36 for the combustion liner 20 and for theplurality of chutes 30. The ceramic matrix composite body 50 may includethe combustion liner 20 and the chutes 30. Forming the ceramic matrixcomposite body 50 may comprise chemical vapor infiltration, slurryinfiltration, or melt infiltration into the ceramic preform 34.

In some examples, enlarging the aperture 32 in the ceramic preform 34with the layup tool 40 may include shaping the aperture 32 into thelarger chute shape with the layup tool 40. The layup tool 40 may includea cylinder. The aperture 32 may be enlarged when the cylinder isinserted into the aperture 32. Alternatively or in addition, enlargingthe aperture 32 in the ceramic preform 34 with the layup tool 40 mayinclude moving ceramic fibers 22 in the ceramic preform 34 such that theceramic fibers 22 extend from the combustion liner 20 into the chute 30in the ceramic matrix composite body 50.

Each component may include additional, different, or fewer components.For example, the ceramic matrix composite body 50 may include more thanone chute 30 or more than one combustion liner 20. Alternatively or inaddition, the layup tool 40 may include multiple components, such as thecylinder and a handle.

To clarify the use of and to hereby provide notice to the public, thephrases “at least one of <A>, <B>, . . . and <N>” or “at least one of<A>, <B>, . . . <N>, or combinations thereof” or “<A>, <B>, . . . and/or<N>” are defined by the Applicant in the broadest sense, superseding anyother implied definitions hereinbefore or hereinafter unless expresslyasserted by the Applicant to the contrary, to mean one or more elementsselected from the group comprising A, B, . . . and N. In other words,the phrases mean any combination of one or more of the elements A, B, .. . or N including any one element alone or the one element incombination with one or more of the other elements which may alsoinclude, in combination, additional elements not listed.

While various embodiments have been described, it will be apparent tothose of ordinary skill in the art that many more embodiments andimplementations are possible. Accordingly, the embodiments describedherein are examples, not the only possible embodiments andimplementations.

Furthermore, the advantages described above are not necessarily the onlyadvantages, and it is not necessarily expected that all of the describedadvantages will be achieved with every embodiment.

What is claimed is:
 1. A combustion assembly for a gas turbine engine,the combustion assembly comprising: a ceramic matrix composite combustorshell comprising: a chamber defined by a wall of the ceramic matrixcomposite combustor shell, and a ceramic matrix composite chute integralwith the ceramic matrix composite combustor shell, wherein the ceramicmatrix composite chute extends towards a midline of the chamber of theceramic matrix composite combustor shell.
 2. The combustion assembly ofclaim 1, wherein the ceramic matrix composite combustor shell is acombustor.
 3. The combustion assembly of claim 1, wherein the ceramicmatrix composite combustor shell is a ceramic matrix composite linerconfigured to mount to a combustor and be disposed in a chamber of thecombustor when mounted to the combustor.
 4. The combustion assembly ofclaim 1, wherein the ceramic matrix composite combustor shell and theceramic matrix composite chute comprise ceramic fibers that extend fromthe ceramic matrix composite combustor shell into the ceramic matrixcomposite chute.
 5. The combustion assembly of claim 1, wherein theceramic matrix composite combustor shell and the ceramic matrixcomposite chute form one continuous unit.
 6. The combustion assembly ofclaim 1, wherein the ceramic matrix composite combustor shell is coupledto the ceramic matrix composite chute without welding or brazing.
 7. Thecombustion assembly of claim 1, wherein the ceramic matrix compositechute defines a chute opening into the chamber that is in a planesubstantially parallel with a plane that is tangent to the ceramicmatrix composite combustor shell where the ceramic matrix compositechute and the ceramic matrix composite combustor shell intersect.
 8. Amethod for fabricating a ceramic matrix composite chute, comprising:forming a porous ceramic preform comprising a plurality of ceramicfibers; forming an aperture in the porous ceramic preform; enlarging theaperture into a chute shape by inserting a layup tool into the aperture;and forming the porous ceramic preform into a ceramic matrix compositebody, the ceramic matrix composite body comprising a combustor shell anda chute.
 9. The method of claim 8, wherein forming the porous ceramicpreform comprises stacking a plurality of two-dimensional weaves orunidirectional tape layups.
 10. The method of claim 9, wherein formingthe aperture in the porous ceramic preform comprises forming an openingin each two-dimensional weave or unidirectional tape layup and aligningthe openings in the stacked plurality of two-dimensional weaves orunidirectional tape layups.
 11. The method of claim 8, wherein formingthe aperture in the porous ceramic preform comprises cutting theaperture into the porous ceramic preform.
 12. The method of claim 8,wherein forming the aperture in the porous ceramic preform comprisesweaving the aperture into the porous ceramic preform.
 13. The method ofclaim 8, wherein forming the porous ceramic preform into the ceramicmatrix composite body comprises treating the porous ceramic preform withone or more of a chemical vapor infiltration, a slurry infiltration, ora melt infiltration.
 14. The method of claim 8, wherein the chutedefines a chute opening into a chamber that is scarfed.
 15. A method forfabricating a ceramic matrix composite chute, comprising: forming aceramic preform into a frame for a combustor shell and a chute; andforming the ceramic preform into a ceramic matrix composite body, theceramic matrix composite body comprising the combustor shell and thechute.
 16. The method of claim 15 further comprising enlarging anaperture in the ceramic preform with a layup tool.
 17. The method ofclaim 16, wherein the layup tool includes a cylinder, the aperture isenlarged when the cylinder is inserted into the aperture.
 18. The methodof claim 16 further comprising moving ceramic fibers in the ceramicpreform with the layup tool when enlarging the aperture such that theceramic fibers extend from the combustor shell into the chute in theceramic matrix composite body.
 19. The method of claim 15, whereinforming the ceramic preform comprises forming the ceramic preform intothe frame for the combustor shell and for a plurality of chutes, and,wherein the ceramic matrix composite body comprises the combustor shelland the chutes.
 20. The method of claim 15 wherein forming the ceramicmatrix composite body comprises one or more of a chemical vaporinfiltration, a slurry infiltration, or a melt infiltration.